CN114560075B - A dynamic adjustment device for the center of mass of a composite aircraft - Google Patents

Abstract

The invention discloses a dynamic mass center adjusting device for a single body of a combined aircraft, which belongs to the technical field of aerospace and particularly comprises a gear, a rack, a motor and a roller. The motor is fixedly connected with the front baffle through the motor frame, the front baffle is fixedly connected with the rear baffle through the connecting rod, two rollers are symmetrically distributed on the front baffle and the rear baffle respectively, and the rollers can roll on the upper surface of the rack groove. The device drives the gear to roll on the rack through the motor, and drives the roller to roll on the upper surface of the rack groove to realize the adjustment of the mass center. The invention has the characteristics of small volume, high integration level, simple and reliable structure and the like, and can realize the adjustment of the single mass center of the combined aircraft.

Description

A dynamic adjustment device for the center of mass of a composite aircraft

technical field

The invention relates to the field of aerospace technology, in particular to a dynamic adjustment device for a single center of mass of an assembled aircraft.

Background technique

For a combined unmanned combat platform with long endurance, long range, and large load requirements, it is divided into two parts: the main body at the core node position and the two wings that can be decomposed into two isomorphic units. In order to enable the two-wing monomer to have an independent adjustment strategy for the aerodynamic characteristics during pre-separation, it is necessary to set up a monomer center-of-mass adjustment device, specifically to set the drive components, control components, energy components and other high-mass components as the active parts inside the two-wing monomer , so that the relative position between the center of mass of the individual airfoil section and the center of aerodynamic pressure can be adjusted.

Under a fixed aerodynamic shape design, the change of the position of the center of mass of the aircraft monomer not only affects the static aerodynamic characteristics such as the angle of attack, drag characteristics, and lift-to-drag ratio of the aircraft, but also affects the dynamic aerodynamic characteristics such as roll and yaw dynamic stability. Precise configuration is the key factor to determine the safe and accurate flight of the aircraft.

For aircraft using variable center of mass control technology, the current research at home and abroad mainly focuses on the research of variable center of mass dynamics and variable center of mass control methods. use simultaneously. Moreover, the existing variable center of mass ball screw actuating device has a complex and redundant structure, occupies a large volume, and has many transmission links, which greatly reduces the stiffness and transmission efficiency of the entire system. In addition, once an excessive load occurs, it will cause a radial load on the ball screw pair in the system, which will greatly cause the screw to be stuck or even damaged, reducing the reliability of the system.

Contents of the invention

The purpose of the present invention is to solve the problems in the above-mentioned background technology, and propose a dynamic adjustment device for the center of mass of the combined aircraft unit, which realizes the change of the center of mass of the entire aircraft unit by controlling the reciprocating motion of the mass block by a motor. Air rudders and reaction attitude control engines are not required, and a pure variable center of mass control method is used to control the pitch and roll attitude of the aircraft to ensure the flight stability of the aircraft. It should be pointed out that the shape designs of the combined aircraft and single-body aircraft described in subsequent illustrations are for reference only, and not the final state. This invention only introduces the variable center of mass device, and does not involve the aerodynamic shape design of the single-body aircraft.

The present invention is achieved like this:

A single center of mass dynamic adjustment device for a combined aircraft, comprising a gear, a rack, a rack slot, a motor, a roller, a connecting rod, a front baffle, a rear baffle, and a quality block. Specifically, the combined aircraft includes a main body at the core node position and can be decomposed into two isomorphic aircraft monomers, wherein a center of mass adjustment device is arranged inside the aircraft monomer; the center of mass The adjustment device includes a rack, and the upper end of the rack is provided with a gear. The gear is fixedly connected with the output end of the motor, and the gear can be driven by the motor to rotate and roll on the rack; the motor is connected to the front baffle through the motor frame. Fixed connection, the front baffle and the rear baffle are fixedly connected by two connecting rods;

The lower end of the rack is provided with a rack groove, the rack is placed in the rack groove, slide rails are provided on both sides of the rack groove, and the front baffle and the rear baffle are on both sides of the rack groove. slides on the rails.

Furthermore, four identical center-of-mass adjustment devices are arranged inside the single aircraft body, and the rack grooves of the four center-of-mass adjustment devices are distributed in a rhombus shape.

Further, there are four symmetrical rollers on the inner sides of the front baffle and the rear baffle, and the four rollers can roll on the plane of the upper surface of the rack groove.

Further, two lighter mass blocks are set to be fixed on the outside of the front baffle, and a heavier mass block is set to be fixed on the outside of the rear baffle; and the two lighter mass blocks, the motor, and the motor frame on the outside of the front baffle The total mass of is equal to the mass of the heavier mass on the outside of the tailgate.

Further, the aircraft monomer has a span length of 1 m, a chord length of 0.5 m, and a maximum take-off weight of 35 kg.

The beneficial effects of the present invention and prior art are:

1. The center-of-mass dynamic adjustment device provided by the present invention is small in size and light in weight. The motor, baffle, roller and gear are designed in one-piece structure. It not only acts as a part of the moving mass, but also has a high degree of integration, which greatly reduces the volume of the entire system;

2. Adopt rack and pinion transmission design, fewer transmission links, high efficiency and strong rigidity. Compared with the traditional ball screw mechanism, the heavy parts such as screw nuts and workbenches are reduced, which greatly improves the flexibility of the whole system;

3. High reliability under load conditions. Compared with the traditional center-of-mass adjustment mechanism, this device is mainly loaded by four rollers, which weakens the radial force load of the gear to the greatest extent, and greatly improves the life of the rack and pinion. Therefore, this device is suitable for complex load capacity Stronger and more reliable.

Description of drawings

Figure 1 is a schematic diagram of the combined aircraft as a whole and its single structure.

Fig. 2 is a structural schematic diagram of a dynamic adjustment device for a combined aircraft center of mass of the present invention;

Fig. 3a is the A-A direction view of Fig. 2 of the dynamic adjustment device for the combined aircraft center of mass of the present invention; Fig. 3b is the B-B sectional view of the B-B direction of Fig. 2 for the dynamic adjustment device of the combined aircraft center of mass of the present invention;

Fig. 4a is a schematic diagram of the distribution of the center of mass dynamic adjustment device of a combined aircraft of the present invention; Fig. 4b is a schematic diagram of the distribution of the center of mass adjustment device inside the aircraft;

Figure 5a is a schematic diagram of the distribution of the center of mass adjustment device when the aircraft adjusts the pitch; Figure 5b is a schematic distribution diagram of the center of mass adjustment device when the aircraft adjusts the roll;

Fig. 6a is a two-dimensional schematic diagram of the center of mass change range of a dynamic adjustment device for the center of mass of a combined aircraft of the present invention; Fig. 6b is a three-dimensional axonometric view of the change range of the center of mass of the dynamic adjustment device for the center of mass of a combined aircraft of the present invention;

Among them, 1-center of mass adjustment device, 2-gear, 3-rack, 4-rack slot, 501-motor, 502-motor frame, 6-roller, 7-connecting rod, 801-front baffle, 802-rear Baffle, 9-mass.

Detailed ways

In order to make the object, technical solution and effect of the present invention clearer and clearer, the following examples are given to further describe the present invention in detail. It should be pointed out that the specific implementations described here are only used to explain the present invention, not to limit the present invention.

As shown in Figure 1, it is a schematic diagram of the overall structure of the combined aircraft and its monomer structure, which can be divided into a main body at the core node position and two wings that can be decomposed into two isomorphic monomers. The center of mass of the present invention is dynamically adjusted. The device 1 is located inside the monocoque.

As shown in Figure 2, a dynamic adjustment device for a combined aircraft monomer center of mass of the present invention includes a gear 2, a rack 3, a rack slot 4, a motor 501, a motor frame 502, a roller 6, a connecting rod 7, and a front baffle 801 , rear baffle 802 , mass block 9 ; the motor 501 is fixedly connected with the front baffle 801 through the motor frame 502 , and the front baffle 801 is fixedly connected with the rear baffle 802 through two connecting rods 7 . The gear 2 is fixedly connected with the output shaft of the motor 501 through a top screw, the gear 2 and the rack 3 have the same width, the gear 2 can be driven by the motor 501 to rotate and roll on the rack 3; the rack 3 is placed in the rack groove 4 Inside, slide rails are provided on both sides of the rack groove 4, and the front baffle plate 801 and the rear baffle plate 802 can slide in the slide rails on both sides of the rack groove.

As shown in Figure 2, two lighter mass blocks 9 are fixed on the outside of the front baffle 801, and the heavier mass block is fixed on the outside of the rear baffle 802; and the front baffle 801, two lighter The total mass of the mass block 9, the motor 501 and the motor frame 502 is equal to the mass mass of the heavier mass block on the outside of the tailgate 802.

As shown in Figures 2 to 3, the four rollers 6 are symmetrically distributed on the inner side of the front baffle 801 and the rear baffle 802 respectively, and are respectively fixed on the baffles through screw connections, and the four rollers 6 can be mounted on the upper surface of the rack groove 4. Rolling on the plane, as shown in Figure 3b.

As shown in Figure 4a~b, it is a schematic diagram of the distribution of the center of mass dynamic adjustment device, where the direction of the x-axis is the span direction of the aircraft, and the direction of the y-axis is the chord direction of the aircraft; there are four identical center-of-mass adjustment devices inside a single aircraft monomer. The racks are distributed inside the aircraft in a rhombus shape.

As shown in Figures 5a-b, they are respectively a schematic diagram of movement of the center-of-mass adjustment device when the aircraft adjusts pitch and roll.

As shown in Figure 6a~b, it is a schematic diagram of the center of mass change range of the center of mass dynamic adjustment device. In this embodiment, it is assumed that the maximum length of the diamond rack in the chord direction (Y-axis direction) is 0.3m, and the maximum length in the span direction (X-axis direction) is 0.7m, the variation range of the center of mass of the four center-of-mass adjustment devices is shown in the shaded part in Figure 5. Assuming that the total mass of the combined aircraft is 35kg, the span length and chord length are 0.5m and 1m respectively, and the mass of each of the four center-of-mass adjustment devices is 3kg, the maximum change in the span direction (X-axis direction) of the overall aircraft monomer is 12mm , the maximum change in the chord direction (Y-axis direction) is 5.142mm.

The above description is only a preferred embodiment of the present invention. It should be pointed out that for those of ordinary skill in the art, without departing from the principle of the present invention, some improvements can also be made, and these improvements should also be regarded as the present invention. protection scope of the invention.

Claims (3)

1. A dynamic adjustment device for the center of mass of a composite aircraft monomer, the composite aircraft includes a main body at the core node position and can be decomposed into two isomorphic aircraft monomers, it is characterized in that the aircraft monomer A center-of-mass adjustment device (1) is arranged inside; The center-of-mass adjustment device (1) includes a rack (3), the upper end of the rack (3) is provided with a gear (2), and the gear (2) is fixedly connected to the output end of the motor (501), The gear (2) can be driven by the motor (501) to rotate and roll on the rack; the motor (501) is fixedly connected with the front baffle (801) through the motor bracket (502), and the front baffle (801) It is fixedly connected with the tailgate (802) through two connecting rods (7); The lower end of the rack (3) is provided with a rack groove (4), the rack (3) is placed in the rack groove (4), and slide rails are arranged on both sides of the rack groove (4). The front baffle (801) and the rear baffle (802) slide in the slide rails on both sides of the rack groove (4); the inside of the individual aircraft monomer is provided with four identical center-of-mass adjustment devices (1), The rack grooves (4) of the four center-of-mass adjustment devices (1) are distributed in a diamond shape; the inner sides of the front baffle (801) and the rear baffle (802) are respectively symmetrical with four rollers (6), and the four rollers (6) It can roll on the plane of the upper surface of the rack groove (4). 2. The dynamic adjustment device for a combined aircraft monomer center of mass according to claim 1, wherein two lighter mass blocks (9) are set to be fixed on the outside of the front fender (801), and a heavier mass block is set. The mass block is fixed on the outside of the rear baffle (802); ) are of equal mass to the heavier mass on the outside. 3. The dynamic adjustment device for the center of mass of a combined aircraft monomer according to claim 1, wherein the aircraft monomer has a span length of 1 m, a chord length of 0.5 m, and a maximum take-off weight of 35 kg.

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